Modular reconfigurable satellite platform supporting on-orbit assembly

Abstract

The application discloses a modular reconfigurable satellite platform supporting on-orbit assembly, which comprises a propulsion cabin, a service cabin, a load cabin, a flexible solar wing, an ion thruster, a mechanical arm and an expandable heat radiator; the propulsion cabin, the service cabin and the load cabin are connected in series to form a cabin section of the satellite platform; the ion thruster is installed on the north-south side of the propulsion cabin; the flexible solar wing is installed on the north-south side of the service cabin; four sets of mechanical arms are installed on the east-west side of the service cabin; and the expandable heat radiator is installed on the side of the load cabin. The modular reconfigurable satellite platform supporting on-orbit assembly adopts modular design and interface standardization design, solves the physical nesting problem among various subsystems of an integrated satellite, supports on-orbit assembly and on-orbit maintenance, and can form a functional complete satellite based on batch launching and on-orbit assembly.

Description

TECHNICAL FIELD

[0001] The application belongs to the technical field of spaceflight, and particularly relates to a modular reconfigurable satellite platform supporting on-orbit assembly. BACKGROUND

[0002] The on-orbit assembly satellite is composed of multiple isomorphic modules (each module has the same function) or heterogeneous modules (each module has different functions) with the same size, and has a universal interface standard and a standard module library based on modular design. The on-orbit assembly satellite can be designed by rapid combination for different tasks, uses a common platform standard, has a plug-and-play function, can be independently upgraded, reconfigured, added, removed or exchanged, and can be repeatedly used in multiple tasks. The modular reconfigurable satellite has the advantages of flexible organization, convenient maintenance operation and strong adaptability, and can effectively improve the maintainability of space systems, reduce the construction cost of space systems, and meet the multi-task requirements of space applications.

[0003] The research on modular reconfigurable satellites has a long history internationally. In 1980, the United States developed the solar maximum mission satellite assembled by multi-task modular satellites (MMS). In 2002, the Goddard Space Flight Center (GSFC) of NASA proposed the "MARS" (Modular, Adaptive, Reconfigurable System) concept for space exploration, and applied it to the design of the lunar orbiter in 2004. In 2007, the U.S. Defense Advanced Research Projects Agency (DARPA) launched the F6 project to develop a future-oriented, fast, flexible, free-flying, fractionated spacecraft (Future, Fast, Flexible, Free-Flying, Fractionated), which was a key project of the "Rapid Response Space Program". At the same time, the University of Tokyo proposed the concept of a reconfigurable space system, which is composed of cell satellites and on-orbit service robots. The cell satellites realize remote sensing, communication and other functions, and are composed of multiple cell units similar to building blocks, with a reconfigurable architecture. The iBOSS project was researched by the Berlin Institute of Technology with the support of the German Aerospace Research Institute. The focus of the project is to decompose the traditional satellite platform into multiple identical building blocks, each building block containing specific functions, adopting standardized design, and assembling into the required space system by a space manipulator. In 2013, Northrop Grumman completed the assembly, integration and testing of the first modular spacecraft (MSV) bus, marking the completion of its functional testing. The MSV is the first modular, rapidly reconfigurable spacecraft.

[0004] In summary, the modular reconfigurable satellite platform should adopt modular design, support on-orbit assembly, reconfiguration, on-orbit maintenance and service, which puts forward new requirements for the satellite platform configuration. The traditional satellite platform configuration design, including box plate type, bearing cylinder type or truss type, is a closed integrated configuration, which cannot meet the requirements of modular reconfiguration. SUMMARY

[0005] The technical problem of the present application is to overcome the shortcomings of the prior art, and to provide a modular reconfigurable satellite platform supporting on-orbit assembly, which adopts modular design and interface standardization design, solves the physical nesting problem between the subsystems of the integrated satellite, thereby supporting on-orbit assembly, on-orbit maintenance, and forming a functional complete satellite based on batch launch and on-orbit assembly.

[0006] In order to solve the above technical problems, the present application discloses a modular reconfigurable satellite platform supporting on-orbit assembly, comprising: a propulsion cabin, a service cabin, a payload cabin, a flexible solar wing, an ion thruster, a mechanical arm and an expandable heat radiator.

[0007] The propulsion cabin, the service cabin and the payload cabin are connected in series to form the cabin section of the satellite platform.

[0008] The ion thruster is installed on the north-south side of the propulsion cabin.

[0009] The flexible solar wing is installed on the north-south side of the service cabin, and four mechanical arms are installed on the east-west side of the service cabin.

[0010] The expandable heat radiator is installed on the side of the payload cabin.

[0011] In the above-mentioned modular reconfigurable satellite platform supporting on-orbit assembly, the propulsion cabin is the main bearing structure, and the structure form is truss structure; the service cabin and the payload cabin are both box plate structures; six hard points are used to connect the propulsion cabin and the service cabin, which can meet the requirements of single-cabin independent assembly, independent hoisting and independent assembly; the star-rocket docking surface adopts a point separation unlocking device.

[0012] In the above-mentioned modular reconfigurable satellite platform supporting on-orbit assembly, the propulsion cabin comprises: a main bearing frame, a propulsion cabin peripheral structure plate, an upper frame, two oxygen tanks, two fuel tanks, two xenon gas bottles, two helium gas bottles and a propulsion cabin standard module.

[0013] The main bearing frame comprises: a docking ring, a main partition, four inclined partition plates and a back floor; wherein the main partition and the four inclined partition plates are staggered and arranged on the back floor and fixed by the docking ring.

[0014] The peripheral structural plates of the propulsion module include: the south plate of the propulsion module, the north plate of the propulsion module, the east plate of the propulsion module, and the west plate of the propulsion module; among them, the south plate of the propulsion module, the north plate of the propulsion module, the east plate of the propulsion module, and the west plate of the propulsion module are respectively arranged on the south side, north side, east side, and west side of the main load-bearing framework;

[0015] The upper frame is arranged on the top of the main load-bearing framework to maintain the support of the peripheral structural plates of the propulsion module;

[0016] Two oxygen tanks, two fuel tanks, and two xenon gas cylinders are arranged on the docking ring and separated by the main partition and 4 inclined partitions; the tops of the two oxygen tanks, two fuel tanks, and two xenon gas cylinders are connected to the two-cabin joint through tie rods; two helium gas cylinders are installed on the back floor; the standard module of the propulsion module and the ion thruster are installed on the outer surfaces of the north and south plates of the propulsion module.

[0017] In the above modular reconfigurable satellite platform supporting on-orbit assembly,

[0018] The main partition adopts the beam-slab composite technology, and the space of the rod and the plate is shared; among them, the rod is made of high-modulus composite materials to form a planar truss system to transfer most of the loads; the plate adopts a honeycomb sandwich panel to facilitate the installation of equipment and propulsion pipelines to match the relatively high-rigidity truss rod system and the high-stress area at the connection with the joint.

[0019] The inclined partition adopts a beam-slab composite structure, the overall shape is an inverted trapezoid, and it contains a truss unit; the inclined partition is provided with lightening holes in the closed area formed by the truss rod system; the inclined partition adopts the means of externally pasting reinforced skins in the area of the embedded rod and the joint area for strengthening design to reasonably disperse the stress and avoid local stress concentration; the end of the inclined partition rod is lined with a cushion block to achieve one-time curing forming with the inclined partition and connection with other components.

[0020] The back floor includes: an outer back floor (1031) and an inner back floor (1032); among them, the inner back floor (1032) is located at the center of the outer back floor (1031), and two helium gas cylinders are installed on the outer back floor (1031);

[0021] The docking ring is circular, and the cross-sectional shape is I-shaped.

[0022] In the above modular reconfigurable satellite platform supporting on-orbit assembly, the service module adopts a box-panel structure, including: the peripheral structural plates of the service module, the upper plate of the service module, the middle plate of the service module, the lower plate of the service module, the partition of the service module, and the standard module of the service module;

[0023] The upper plate of the service module, the middle plate of the service module, the lower plate of the service module, and the partition of the service module form a "艹" shaped structure; among them, the bottom of the "艹" shaped structure is connected to the propulsion module;

[0024] The peripheral structural plates of the service module include: the east plate of the service module, the west plate of the service module, the south plate of the service module, and the north plate of the service module; among them, the east plate of the service module, the west plate of the service module, the south plate of the service module, and the north plate of the service module are respectively arranged on the east side, west side, south side, and north side of the "艹"-shaped structure;

[0025] The east and west plates of the service module are of an open structure, which is used to realize the storage, grasping, movement, and replacement of the platform service unit modules;

[0026] Service module standard modules are installed on the outer surfaces of the north and south plates of the service module and on the east and west partitions inside the service module; among them, 60 service module standard modules are arranged on the outer surfaces of the south and north plates of the service module, and 64 service module standard modules are arranged inside the cabin;

[0027] Flexible solar wings are installed on the outer surfaces of the north and south plates of the service module through standard interfaces;

[0028] Two sets of robotic arms are configured on the outer surfaces of the east and west plates of the service module to meet the requirements of on-orbit assembly operations.

[0029] In the above-mentioned modular reconfigurable satellite platform supporting on-orbit assembly, the payload module includes: a payload module dispenser, a payload module docking adapter, and a payload module standard module; among them, the main structure of the payload module is the payload module dispenser with a cabin plate nested truss structure, and payload module docking adapters are installed on the north and south sides at the lower end of the payload module dispenser; the payload module docking adapter is mainly of a box plate type, and the internal truss members and joints are adhesively bonded into a whole.

[0030] In the above-mentioned modular reconfigurable satellite platform supporting on-orbit assembly,

[0031] The payload module dispenser is used to provide an installation interface for the payload module standard module in the launch state;

[0032] The payload module docking adapter is used to provide an installation interface for the payload module standard module after the satellite is deployed in orbit.

[0033] In the above-mentioned modular reconfigurable satellite platform supporting on-orbit assembly, in the launch state, 4 standard payload units, 2 sets of deployable thermal radiators, a ground sensitivity function module, and a TT&C antenna function module are arranged on the payload module dispenser; after being in orbit, the payload module docking adapter supports on-orbit assembly and expansion to form a "cross"-shaped on-orbit configuration.

[0034] In the above-mentioned modular reconfigurable satellite platform supporting on-orbit assembly, the flexible solar wings, ion thrusters, robotic arms, and deployable thermal radiators adopt modular design and are connected to the platform through standardized interfaces, supporting replaceability and maintenance.

[0035] In the above-mentioned modular reconfigurable satellite platform supporting on-orbit assembly, [[ID=The flexible solar wing adopts a circular flexible wing, has a diameter of 15 meters in an unfolded state, and has a height of 5109.2 mm and a width of 1402.1 mm in a folded state;

[0037] A pair of 10-meter and a pair of 4-meter mechanical arms are installed on the east and west sides of the service cabin respectively, the two pairs of mechanical arms can be connected in series to realize on-orbit grabbing and replacement of the modules;

[0038] A set of expandable heat radiators is arranged on the east and west sides of the load cabin respectively, each set of expandable heat radiators comprises four heat radiation plates, adopts a folding structure similar to a solar wing, and is compressed on the east and west sides of the load cabin.

[0039] Four groups of ion thrusters are installed on the lower edges of the outer surfaces of the north and south panels of the propulsion cabin through standard modules, the ion thrusters are connected with the standard modules of the propulsion cabin through two-axis mechanisms, and in the firing state, the ion thrusters are compressed on the outer surfaces of the north and south panels of the propulsion cabin.

[0040] The present application has the following advantages:

[0041] (1) The present application discloses a modular reconfigurable satellite platform supporting on-orbit assembly, which adopts compartmentalization and modularization design, and is divided into a propulsion cabin, a service cabin and a load cabin, the propulsion cabin is a standardized bearing platform, the service cabin and the load cabin adopt modular design, and the satellite is reconfigurable and supports on-orbit assembly.

[0042] (2) The present application discloses a modular reconfigurable satellite platform supporting on-orbit assembly, which takes a truss type propulsion cabin as a main bearing structure, is connected with a service cabin through hard points, and has a standardized connection interface, and is suitable for the modular design of the service cabin.

[0043] (3) The present application discloses a modular reconfigurable satellite platform supporting on-orbit assembly, the service cabin adopts a box plate type structure and a standard module configuration, has high structural space utilization, and part of the open structure facilitates the grabbing and moving of modules, so that the service cabin is reconfigurable, supports on-orbit function expansion and maintenance.

[0044] (4) The present application discloses a modular reconfigurable satellite platform supporting on-orbit assembly, the load cabin adopts a cabin panel nested truss type load distributor and a load standard module configuration, on the one hand, the structural mass is reduced, the structural strength is improved, and the installation interface is considered, on the other hand, sufficient load standard module configuration space is provided; the load distributor has a symmetrical structure, and the load module unit can be assembled on-orbit according to task requirements to realize flexible expansion of the load scale.

[0045] (5) The present application discloses a modular reconfigurable satellite platform supporting on-orbit assembly, which takes a standard module as a basic component unit of a satellite service cabin and a load cabin, the module is connected with the platform or other modules through a standard interface, has flexible assembly capacity, and realizes reconfiguration of the satellite platform and the load. BRIEF DESCRIPTION OF DRAWINGS

[0046] Figure 1 is a disassembled view of a modular reconfigurable satellite platform supporting on-orbit assembly in an embodiment of the application;

[0047] Figure 2 is a configuration view of a propulsion module in an embodiment of the application;

[0048] Figure 3 is a configuration view of a docking ring in an embodiment of the application;

[0049] Figure 4 is a configuration view of a diagonal bulkhead in an embodiment of the application;

[0050] Figure 5 is a configuration view of a dorsal bulkhead in an embodiment of the application;

[0051] Figure 6 is a connection view of a two-module joint location in an embodiment of the application;

[0052] Figure 7 is a configuration view of a service module in an embodiment of the application;

[0053] Figure 8 is a disassembled view of a service module in an embodiment of the application;

[0054] Figure 9 is a configuration view of a payload module in an embodiment of the application;

[0055] Figure 10 is a truss view of a payload distributor in an embodiment of the application;

[0056] Figure 11 is a view of a solar wing in an extended state in an embodiment of the application;

[0057] Figure 12 is a view of a solar wing in a stowed envelope state in an embodiment of the application;

[0058] Figure 13 is a configuration view of a solar wing and its deployment mechanism in an embodiment of the application;

[0059] Figure 14 is a configuration view of a robotic arm in an embodiment of the application;

[0060] Figure 15 is a view of an extendable heat radiator in a stowed state in an embodiment of the application;

[0061] Figure 16 is a view of an extendable heat radiator in an extended state in an embodiment of the application;

[0062] Figure 17 is a schematic diagram of an ion thruster in a launch state according to an embodiment of the present application;

[0063] Figure 18 is a schematic diagram of an ion thruster in an on-orbit state according to an embodiment of the present application. DETAILED DESCRIPTION

[0064] In order to make the objects, technical solutions, and advantages of the present application clearer, the disclosed embodiments of the present application will be described in further detail below with reference to the accompanying drawings.

[0065] One of the core ideas of the present application is to break through the limitations of traditional satellite configuration design and provide a modular reconfigurable satellite platform configuration that supports on-orbit assembly and on-orbit replacement and maintenance. By using modular design and interface standardization design, the physical nesting between the subsystems of an integrated satellite is solved, thereby supporting on-orbit assembly and on-orbit maintenance, and a functional complete GEO large satellite can be formed based on batch launching and on-orbit assembly.

[0066] As Figure 1 In this embodiment, the modular reconfigurable satellite platform supporting on-orbit assembly includes a propulsion cabin 1, a service cabin 2, a payload cabin 3, a flexible solar wing 4, an ion thruster 5, a mechanical arm 6, and a deployable heat radiator 7. The propulsion cabin 1, the service cabin 2, and the payload cabin 3 are connected in series to form the cabin section of the satellite platform. The ion thruster 5 is installed on the north-south side of the propulsion cabin 1. The flexible solar wing 4 is installed on the north-south side of the service cabin 2. The four mechanical arms 6 are installed on the east-west side of the service cabin 2. The deployable heat radiator 7 is installed on the side of the payload cabin 3.

[0067] In this embodiment, the propulsion cabin 1 is the main load-bearing structure and has a truss structure. The service cabin 2 and the payload cabin 3 are both box plate structures. Six hard points are used to connect the propulsion cabin 1 and the service cabin 2, which can meet the requirements of single-cabin independent assembly, independent hoisting, and independent final assembly. A point separation unlocking device is used for the satellite-rocket interface.

[0068] The structures of the propulsion cabin 1, the service cabin 2, the payload cabin 3, the flexible solar wing 4, the ion thruster 5, the mechanical arm 6, and the deployable heat radiator 7 will be described in detail below.

[0069] Propulsion Cabin

[0070] In this embodiment, as Figure 2The propulsion cabin 1 can specifically include a main load-bearing framework, a propulsion cabin peripheral structural plate, an upper frame 108, two oxygen tanks, two fuel tanks, two xenon gas bottles, two helium gas bottles, and a propulsion cabin standard module. Further, the main load-bearing framework can specifically include a docking ring, a main partition plate 101, four inclined partition plates 102, and a back floor 103; the propulsion cabin peripheral structural plate can specifically include a propulsion cabin south plate 104, a propulsion cabin north plate 105, a propulsion cabin east plate 106, and a propulsion cabin west plate 107.

[0071] The main partition plate 101 and the four inclined partition plates 102 are arranged on the back floor 103 in a staggered manner and are fixed by the docking ring. The propulsion cabin south plate 104, the propulsion cabin north plate 105, the propulsion cabin east plate 106, and the propulsion cabin west plate 107 are respectively arranged on the south side, the north side, the east side, and the west side of the main load-bearing framework. The upper frame 108 is arranged on the top of the main load-bearing framework to support the propulsion cabin peripheral structural plate. The two oxygen tanks, the two fuel tanks, and the two xenon gas bottles are arranged on the docking ring and are separated by the main partition plate 101 and the four inclined partition plates 102. The top of the two oxygen tanks, the two fuel tanks, and the two xenon gas bottles is connected to the two-cabin joint by a pull rod. The two helium gas bottles are installed on the back floor 103. The propulsion cabin standard module and the ion thruster 5 are installed on the outer surface of the propulsion cabin north-south plate.

[0072] The main load-bearing framework is a three-dimensional truss load-bearing system composed of three groups of “W”-shaped planar trusses in the propulsion cabin, including the docking ring, the main partition plate 101, the four inclined partition plates 102, and the back floor 103. The three groups of planar trusses can meet the basic frequency requirements of carrying satellites and can provide a relatively large number of two-cabin connection points, facilitating adaptation to different types of payloads. The lower end nodes of the planar trusses are connected to the docking ring, and the upper end nodes form a central joint and a two-cabin joint, respectively.

[0073] As shown in FIG. 1, Figure 3 The docking ring is circular and has an I-shaped cross-section. There are six local connections between the truss nodes and the docking ring and six local connections between the storage tanks and the docking ring. To transfer and bear large concentrated loads, the flange thickness is thickened. The flange on the docking ring needs to be appropriately widened at the local concentrated force transmission point to adapt to the connection needs of the truss nodes.

[0074] The main partition plate 101 uses beam-plate composite technology, with the beam and the plate sharing space. The beam is made of high-modulus composite material to form a planar truss system to transfer most of the load. The plate is a honeycomb sandwich plate to facilitate the installation of equipment and propulsion pipelines to match the high-stiffness truss rod system and the high-stress area of the local joint connection.

[0075] The inclined bulkhead 102 adopts a beam-plate composite structure, has an overall shape of an inverted ladder type, and contains a truss unit; the inclined bulkhead is provided with lightening holes in a closed area formed by the truss bar system; the inclined bulkhead is strengthened by means of an outer-attached reinforcing skin in the area of the embedded bar and the joint area, so as to reasonably disperse stress and avoid local stress concentration. The end of the inclined bulkhead bar is lined with a pad, so as to realize one-time solidification forming with the inclined bulkhead and connection with other components, center joints, two-cabin joints and butt joint ring joints.

[0076] As shown in Figure 5 , the back floor 103 can specifically include an outer back floor 1031 and an inner back floor 1032. The inner back floor 1032 is located at the center of the outer back floor 1031, and two helium cylinders are mounted on the outer back floor 1031.

[0077] The six "hard points" at the top of the propulsion cabin are the mechanical interface positions of the propulsion cabin and any type of load cabin. The mechanical load of the service cabin is transmitted to the propulsion cabin by designing six two-cabin joints to realize two-cabin connection. In order to improve the mechanical environment of the structure plate, the structure plates at the remaining positions of the two cabins can be selected to be connected, as shown in Figure 6 .

[0078] The service cabin

[0079] As shown in Figure 7 , the service cabin 2 adopts a box plate type structure, and can specifically include a service cabin peripheral structure plate, a service cabin upper plate 201, a service cabin middle plate 202, a service cabin lower plate 203, a service cabin bulkhead 204 and a service cabin standard module. The service cabin upper plate 201, the service cabin middle plate 202, the service cabin lower plate 203 and the service cabin bulkhead 204 form a "radical" shape structure, and the bottom of the "radical" shape structure is connected with the six joints of the propulsion cabin. The service cabin peripheral structure plate can specifically include a service cabin east plate 205, a service cabin west plate 206, a service cabin south plate 207 and a service cabin north plate 208; the service cabin east plate 205, the service cabin west plate 206, the service cabin south plate 207 and the service cabin north plate 208 are arranged at the east side, the west side, the south side and the north side of the "radical" shape structure, respectively.

[0080] Preferably, the east-west plate of the service cabin is an open structure, which is used to realize platform service unit module storage, grabbing movement and replacement. The outer surfaces of the service cabin south plate and the service cabin north plate and the service cabin internal east-west bulkhead are provided with service cabin standard modules; wherein, the outer surfaces of the service cabin south plate and the service cabin north plate are arranged with 60 service cabin standard modules, and the inside of the service cabin is arranged with 64 service cabin standard modules. The outer surfaces of the service cabin south plate and the service cabin north plate are provided with flexible solar wings through standard interfaces. The outer surface of the service cabin east-west plate is configured with two sets of mechanical arms to match the in-orbit assembly operation requirements.

[0081] Preferably, the service cabin is entirely formed by splicing structure plates, and is composed of 10 structure plates and directly attached parts. The exploded view of the service cabin is as shown in Figure 8The service cabin north-south plate is installed with more equipment and has heat dissipation requirements, and the external installation service cabin standard module and flexible solar wing are installed. The service cabin north-south partition plate provides longitudinal support for the upper plate of the service cabin and transverse support for the north-south plate of the upper plate of the service cabin, and installs the service cabin standard module. The service cabin +Y / -Y partition plate provides longitudinal support for the upper plate of the service cabin and transverse support for the east-west plate of the service cabin. The service cabin middle plate 202 provides transverse support and stability for the peripheral structural plate of the service cabin, and provides a closed loop for the upper cabin and the lower cabin. The service cabin upper plate 201, the service cabin middle plate 202 and the service cabin lower plate 203 provide transverse support and stability for the peripheral structural plate of the service cabin, and provide a closed loop for the upper cabin and the lower cabin.

[0082] Payload cabin

[0083] As Figure 9 shown, the payload cabin 3 can specifically include: a payload cabin distributor 301, a payload cabin adapter 302 and a payload cabin standard module 303. The main structure of the payload cabin 3 is a cabin plate nested truss type payload cabin distributor 301, and the payload cabin distributor 301 is installed with the payload cabin adapter 302 on the lower end of the north-south two sides.

[0084] Preferably, the payload cabin distributor 301 is used to provide an installation interface for the payload cabin standard module in a launch state; and the payload cabin adapter 302 is used to provide an installation interface for the payload cabin standard module after the satellite is deployed in orbit. In the launch state, four standard payload units, two groups of expandable heat radiators, one ground-sensitive functional module and one TT&C antenna functional module are arranged on the payload cabin distributor 301; after being in orbit, the payload cabin adapter supports in-orbit assembly expansion to form a “cross” type in-orbit configuration.

[0085] Preferably, in order to reduce the satellite structure mass, improve the structure strength and take into account the installation interface, the payload cabin adapter 302 is mainly in the form of a box plate, and the inside is integrally connected by truss rods and joints, as Figure 10 shown.

[0086] Large component layout

[0087] The flexible solar wing 4, the ion thruster 5, the mechanical arm 6 and the expandable heat radiator 7 and other off-platform large components also adopt modular design and are connected with the platform through a standardized interface, supporting replaceability and maintenance.

[0088] Preferably, the flexible solar wing 4 adopts a circular flexible wing, with a diameter of 15 meters in the expanded state and a height of 5109.2mm and a width of 1402.1mm in the folded state, as Figure 11 , 12 shown. Considering the avoidance of rotating and in-orbit expansion of the load module, the solar wing arm is about 18m long, and considering the requirement of the carrying envelope, the thickness of the solar wing expansion mechanism needs to be controlled, and an expansion mechanism composed of five rods is designed, and five compression points are set, as Figure 13The solar wings are arranged on the propulsion cabin, the south and north panels of the service cabin, the pressing devices are arranged on the standard module units on which the support structures are arranged, and the structures should provide a good mechanical environment for the pressing points.

[0089] Preferably, one pair of 10-meter and one pair of 4-meter mechanical arms are arranged on the east and west sides of the service cabin 2, the two pairs of mechanical arms can be connected in series to realize the on-orbit grabbing and replacement of the modules, for example, Figure 14 as shown in the figure.

[0090] Preferably, one group of expandable heat radiators 7 is arranged on the east and west sides of the load cabin 3, the group of expandable heat radiators includes four heat radiation plates, adopts a folding structure similar to the solar wing, and is pressed on the east and west sides of the load cabin 3, for example, Figure 15 as shown in the figure. The expanded state of the expandable heat radiator is shown in Figure 16 as shown in the figure, which can guarantee the heat dissipation requirements of the first launch satellite platform and the four load modules, and the heat dissipation of the subsequent 12 load modules is performed by the radiators carried by the load modules.

[0091] Preferably, the four groups of ion thrusters 5 are arranged on the lower edges of the outer surfaces of the north and south panels of the propulsion cabin through the standard modules, the ion thrusters 5 are connected to the propulsion cabin standard modules through two-axis mechanisms, in the launching state, the ion thrusters 5 are pressed on the outer surfaces of the north and south panels of the propulsion cabin, for example, Figure 17 as shown in the figure; in the on-orbit state, the ion thrusters 5 are rotated to the target positions through the double-axis mechanisms, for example, Figure 18 as shown in the figure.

[0092] On the basis of the above embodiment, the technology of the application is applied to the configuration design of a certain modular reconfigurable satellite platform, and the configuration design is as follows:

[0093] The certain modular reconfigurable satellite platform is divided into three cabin sections: a propulsion cabin, a service cabin and a load cabin. The ion thrusters are arranged on the north and south sides of the propulsion cabin, the flexible solar wings are arranged on the north and south sides of the service cabin, and four groups of mechanical arms are arranged on the east and west sides of the service cabin; the expandable heat radiators are arranged on the load cabin.

[0094] Propulsion cabin

[0095] The basic size of the propulsion cabin is 2700mm (X) x 2700mm (Y) x 1878mm (Z), which is composed of a main load-bearing frame and a peripheral structural plate, and the top of the propulsion cabin is an upper frame. The main load-bearing frame is composed of a butt joint ring, a main partition plate, four inclined partition plates and a back floor. The butt joint ring is circular, the cross-sectional shape is an I-shaped section, the column segment division circle diameter is 1930mm, and the height is 150mm. The main partition plate adopts beam-plate composite technology, the beam and the plate share the space, the beam is made of high modulus composite material, and the plate is made of honeycomb sandwich plate. The inclined partition plate adopts a beam-plate composite structure, the overall shape is an inverted ladder type, and contains a truss unit. The inclined partition plate and the embedded rod system have the same design state as the main partition plate, and there is no one-way reinforcing plate on both sides of the rod system. The closed area composed of the truss rod system is arranged with lightening holes. The back floor is composed of an outer back floor and an inner back floor. The peripheral structural plate is composed of a propulsion cabin south plate, a propulsion cabin north plate, a propulsion cabin east plate, a propulsion cabin west plate and the like. Four storage boxes and two xenon gas bottles are directly installed on the butt joint ring, and the top is connected with the two cabin joints through a pull rod.

[0096] Service cabin

[0097] The service cabin adopts a box plate type structure, and the basic size is 2700mm x 2700mm x 2300mm. The inside of the service cabin is a "Radical" shaped structure, the bottom of the "Radical" shape is connected with six joints of the propulsion cabin, and the top is connected with the floor. The service cabin is integrally formed by splicing of structural plates, and is composed of 10 structural plates and directly attached parts, the structural plates including a service cabin east plate, a service cabin west plate, a service cabin south plate, a service cabin north plate, a service cabin upper plate, a service cabin middle plate, a service cabin lower plate, a service cabin south partition plate, a service cabin north partition plate, a service cabin +Y partition plate and a service cabin -Y partition plate. The east and west plates of the service cabin are open structures. Standard functional modules are installed on the outer surfaces of the north and south plates of the service cabin and the internal east and west partition plates, wherein 60 standard modules are arranged on the outer surfaces of the north and south plates, and 64 standard modules are arranged inside the cabin. The outer surfaces of the north and south plates are provided with standard interfaces for installing ion thruster modules and solar wing modules, and the outer surface of the east and west plates of the service cabin is provided with a pair of 10-meter mechanical arms and a pair of 4-meter high-precision mechanical arms.

[0098] Payload cabin

[0099] The payload cabin is composed of a payload cabin distributor and a payload cabin butt jointer. The payload cabin distributor is a cabin plate nested truss type structure, mainly in the form of a box plate, and the inside is integrally formed by using truss rods and joints. The outer dimension is 1000mm x 2700mm x 3700mm. The payload cabin distributor is provided with the payload cabin butt jointer on the lower end of the north and south sides, and the outer dimension is 2700mm x 2700mm x 1200mm.

[0100] Flexible solar wing

[0101] The flexible solar wing uses a circular flexible wing, and the diameter of the unfolded state is 15 meters, the height of the folded state is 5109.2 mm, and the width is 1402.1 mm. The flexible solar wing arm is about 18 m long. The flexible solar wing unfolding mechanism is composed of 5 rod systems, and five compression points are arranged. The flexible solar wing is installed on the propulsion cabin, the south plate and the north plate of the service cabin, and the compression device is arranged on the standard module unit, and the support structure is arranged thereon.

[0102] Mechanical arm

[0103] The mechanical arm is installed on the east-west surface of the service cabin, and a total of four sets are configured, one set of 10 meters and one set of 4 meters are installed on the east and west sides, and the two sets of mechanical arms can be connected in series.

[0104] Deployable heat radiator

[0105] The deployable heat radiator is arranged on the east and west sides of the load distributor, and a total of two groups are configured, one group includes four heat radiation panels, adopts a folding structure similar to the solar wing, is compressed on the east and west surfaces of the load distributor, and each panel has a height of 2.5 m, a width of 3 m, and an area of 7.5 m 2 .

[0106] Ion thruster

[0107] The four groups of ion thrusters are installed on the lower edge of the outer surface of the north and south plates of the propulsion cabin through the standard module, the ion thrusters are connected with the standard module through a two-axis mechanism, are compressed on the outer surface of the north and south plates in the emission state, and are rotated to the target position through the two-axis mechanism in the on-orbit state.

[0108] Although the present application has been disclosed with the above preferred embodiments, it is not intended to limit the present application, and any person skilled in the art can make possible changes and modifications to the technical solutions of the present application by using the disclosed methods and technical contents without departing from the spirit and scope of the present application. Therefore, any simple modification, equivalent change and modification made to the above embodiments according to the technical essence of the present application, which does not deviate from the technical solutions of the present application, belongs to the protection scope of the technical solutions of the present application.

[0109] The contents not described in detail in the specification of the present application belong to the known technology of the person skilled in the art.

Claims

1. A modular reconfigurable satellite platform supporting on-orbit assembly, characterized in that, Comprise: propulsion cabin (1), service cabin (2), load cabin (3), flexible solar wing (4), ion thruster (5), mechanical arm (6) and deployable heat radiator (7); Propulsion cabin (1), service cabin (2) and load cabin (3) are connected in series in turn, which constitutes the cabin section of satellite platform; The propulsion cabin (1) is the main load-bearing structure, which is in the form of truss structure; The service cabin (2) and the load cabin (3) are both in the form of box plate structure; Six hard points are used to connect the propulsion cabin (1) and the service cabin (2), which meets the requirements of single cabin independent assembly, independent hoisting and independent assembly; The point separation unlocking device is used for the satellite-rocket interface; The ion thruster (5) is installed on the north-south side of the propulsion cabin (1); The flexible solar wing (4) is installed on the north-south side of the service cabin (2), and the four mechanical arms (6) are installed on the east-west side of the service cabin (2); The deployable heat radiator (7) is installed on the side of the load cabin (3); The propulsion cabin (1) comprises: a main load-bearing framework, a propulsion cabin peripheral structural plate, an upper frame (108), two oxygen tanks, two fuel tanks, two xenon gas bottles, two helium gas bottles and a propulsion cabin standard module; The main load-bearing framework comprises: a docking ring, a main partition plate (101), four inclined partition plates (102) and a back floor (103); wherein, the main partition plate (101) and the four inclined partition plates (102) are staggered and arranged on the back floor (103) and fixed through the docking ring; The propulsion cabin peripheral structural plate comprises: a propulsion cabin south plate (104), a propulsion cabin north plate (105), a propulsion cabin east plate (106) and a propulsion cabin west plate (107); The propulsion cabin south plate (104), the propulsion cabin north plate (105), the propulsion cabin east plate (106) and the propulsion cabin west plate (107) are arranged on the south side, the north side, the east side and the west side of the main load-bearing framework respectively; The upper frame (108) is arranged on the top of the main load-bearing framework to support the propulsion cabin peripheral structural plate; The two oxygen tanks, the two fuel tanks and the two xenon gas bottles are arranged on the docking ring and separated by the main partition plate (101) and the four inclined partition plates (102); The top of the two oxygen tanks, the two fuel tanks and the two xenon gas bottles is connected with the two cabin joints through the pull rod; The two helium gas bottles are installed on the back floor (103); The propulsion cabin standard module and the ion thruster (5) are installed on the outer surface of the propulsion cabin north-south plate. The service cabin (2) comprises a service cabin peripheral structure plate, a service cabin upper plate (201), a service cabin middle plate (202), a service cabin lower plate (203), a service cabin partition plate (204) and a service cabin standard module; the service cabin upper plate (201), the service cabin middle plate (202), the service cabin lower plate (203) and the service cabin partition plate (204) form a "radical” shape structure; the bottom of the "radical” shape structure is connected with the propulsion cabin; the service cabin peripheral structure plate comprises a service cabin east plate (205), a service cabin west plate (206), a service cabin south plate (207) and a service cabin north plate (208); the service cabin east plate (205), the service cabin west plate (206), the service cabin south plate (207) and the service cabin north plate (208) are arranged on the east side, the west side, the south side and the north side of the "radical” shape structure respectively; the service cabin east-west plate is an open structure and is used for realizing platform service unit module storage, grabbing movement and replacement; the service cabin standard module is mounted on the outer surface of the service cabin south-north plate and the service cabin internal east-west partition plate; 60 service cabin standard modules are arranged on the outer surface of the service cabin south-north plate, and 64 service cabin standard modules are arranged in the cabin; the flexible solar wing (4) is mounted on the outer surface of the service cabin south-north plate through a standard interface; two sets of mechanical arms are arranged on the outer surface of the service cabin east-west plate to match the in-orbit assembly operation requirements; The load cabin (3) comprises a load cabin distributor (301), a load cabin adapter (302) and a load cabin standard module (303); wherein the main structure of the load cabin (3) is a cabin plate nested truss type load cabin distributor (301), and the load cabin adapter (302) is mounted on the lower end of the north-south two sides of the load cabin distributor (301); the load cabin adapter (302) is mainly in the form of a box plate, and the inside is integrally connected by truss rods and joints; in the launch state, four standard load units, two groups of expandable heat radiators, one ground sensitive function module and one measurement and control antenna function module are arranged on the load cabin distributor (301); after in-orbit, the load cabin adapter supports in-orbit assembly expansion to form a "cross” type in-orbit configuration.

2. The modular reconfigurable satellite platform supporting in-orbit assembly according to claim 1, wherein The main partition plate (101) adopts a beam-plate composite technology, and the rods and the plates share the space; wherein the rods are made of high modulus composite materials to form a plane truss system and transfer most of the load; the plates are made of honeycomb sandwich plates to facilitate the installation of equipment and propulsion pipelines, so as to match the high-stiffness truss rod system and the high-stress area of the local joint connection; The inclined partition plate (102) adopts a beam-plate composite structure and has an inverted ladder shape and contains a truss unit; the inclined partition plate is provided with lightening holes in the closed area formed by the truss rod system; the inclined partition plate is reinforced by an outer-attached reinforcing skin in the embedded rod area and the joint area to reasonably disperse the stress and avoid local stress concentration; the end of the rod of the inclined partition plate is lined with a pad to realize one-time curing forming with the inclined partition plate and connection with other components. The back floor (103) comprises an outer back floor (1031) and an inner back floor (1032); wherein the inner back floor (1032) is located at the center of the outer back floor (1031), and two helium cylinders are mounted on the outer back floor (1031); The butt joint ring is circular and has a cross-sectional shape of an I-shaped section.

3. The modular reconfigurable satellite platform supporting on-orbit assembly according to claim 1, wherein, The payload cabin distributor (301) is used to provide the mounting interface of the payload cabin standard module in the launch state; The payload cabin adapter (302) is used to provide the mounting interface of the payload cabin standard module after the satellite is deployed on-orbit.

4. The modular reconfigurable satellite platform supporting on-orbit assembly of claim 1, wherein, The flexible solar wing (4), the ion thruster (5), the mechanical arm (6) and the deployable heat radiator (7) adopt a modular design and are connected with the platform through a standardized interface, supporting replacement and maintenance.

5. The modular reconfigurable satellite platform supporting on-orbit assembly according to claim 1, wherein, The flexible solar wing (4) adopts a circular flexible wing, with a diameter of 15 meters in the deployed state, a height of 5109.2 mm and a width of 1402.1 mm in the folded state; One pair of 10-meter and one pair of 4-meter mechanical arms are mounted on the east and west sides of the service cabin (2), and the two pairs of mechanical arms can be connected in series to realize on-orbit grabbing and replacement of modules; A group of deployable heat radiators (7) are arranged on the east and west sides of the payload cabin (3), and each group of deployable heat radiators comprises four heat radiation plates and adopts a folding structure similar to the solar wing, which is compressed on the outer surfaces of the east and west sides of the payload cabin (3); Four groups of ion thrusters (5) are mounted on the lower edges of the outer surfaces of the north-south plates of the propulsion cabin through standard modules, and the ion thrusters (5) are connected with the propulsion cabin standard modules through two-axis mechanisms, which are compressed on the outer surfaces of the north-south plates of the propulsion cabin in the launch state.

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